|Role||Light utility/training aircraft|
|First flight||22 April 1959 (UTVA-56)|
Development and design
In 1959 the Yugoslav aircraft company UTVA designed and built a single-engined, high-winged light utility aircraft, the UTVA 56, with a prototype making the first flight on 22 April 1959. Testing was successful, but the aircraft was redesigned for production, with a more powerful Lycoming O-480 engine, and designated the UTVA-60.
The UTVA-60 is an all-metal, four-place, strut-braced high-wing monoplane. It is fitted with a fixed conventional undercarriage which uses cantilevered steel tube struts. Trailing-edge wing flaps are linked to the ailerons, drooping the ailerons when the flaps are lowered to reduce landing speed, while the agricultural version's wing was fitted with slots.
The UTVA-60 was used as the basis for the UTVA-65, a specialised agricultural aircraft, which used the wings, undercarriage and tail of the UTVA-60, but with a low-mounted wing. The UTVA-60 was replaced in production by the UTVA-66, a further improved version.
- Prototype, powered by a 194 kW (260 hp) Lycoming GO-435 engine.
- Basic four seat utility version.
- Dual control version.
- Agricultural version.
- Ambulance version.
- Floatplane, powered by a 221 kW (296 kW) Lycoming GO-480-G1H6 engine.
Data from Jane's All The World's Aircraft 1965-66; Mondey
- Crew: 1
- Capacity: 3 passengers/2 stretchers and attendant
- Length: 8.22 m (27 ft 0 in)
- Wingspan: 11.40 m (37 ft 5 in)
- Height: 2.72 m (8 ft 11 in)
- Wing area: 18.08 m2 (194.6 sq ft)
- Aspect ratio: 7.19
- Airfoil: NACA 4412 (modified)
- Empty weight: 952 kg (2,099 lb)
- Max takeoff weight: 1,620 kg (3,571 lb)
- Powerplant: 1 × Lycoming O-480-G1H6 air-cooled flat-six, 201 kW (270 hp)
- Propellers: 2-bladed Hartzell HC-A2X20-1B/10133-3 constant speed metal propeller
- Maximum speed: 252 km/h (157 mph; 136 kn) at sea level
- Cruise speed: 230 km/h (143 mph; 124 kn)
- Stall speed: 73 km/h (45 mph; 39 kn)
- Never exceed speed: 300 km/h (186 mph; 162 kn)
- Range: 780 km (485 mi; 421 nmi)
- Service ceiling: 5,200 m (17,100 ft)
- Rate of climb: 6.40 m/s (1,260 ft/min)
- Wing loading: 89.60 kg/m2 (18.35 lb/sq ft)
- Related development
- Taylor 1965, p.344.
- "UTVA 56 / 60 Aircraft history performance and specifications". Pilotfriend. Retrieved 21 December 2009.
- Flight 25 September 1959, p.305.
- Donald 1997, p.887.
- Hayles, John. "Yugoslavia Air Force: Aircraft Types". Aeroflight. 1 July 2004. Retrieved 21 December 2009.
- Forsgren, Jan. "Aviation Royale Khmere/Khmer Air Force Aircraft". Aeroflight. 22 April 2007. Retrieved 21 December 2009.
- Grandolini 1988, p. 43.
- Donald, David (ed.) The Encyclopedia of World Aircraft. Leicester, UK: Blitz Editions, 1997. ISBN 1-85605-375-X.
- Grandolini, Albert. "L'Aviation Royale Khmere: The first 15 years of Cambodian military aviation". Air Enthusiast, Thirty-seven, September–December 1988. Bromley, UK:Fine Scroll. ISSN 0143-5450. pp. 39–47 .
- Sport and Business Flight, 25 September 1959, p. 305.
- Taylor, John W. R. Jane's All The World's Aircraft 1965-66. London: Samson Low, Marston, 1965.
- Mondey, David, Encyclopedia of The World's Commercial and Private Aircraft, Crescent Books, New York NY (1981), p. 241
|Wikimedia Commons has media related to UTVA aircraft.|
- UTVA-60 (in Russian)